Asymmetric gear teeth for gearbox
AssigneePratt & Whitney Canada Corp.
InventorDaniel Harvey
Life of this patent
Estimating the term…
Abstract
A spur gear of a gearbox of a gas turbine engine system of an aircraft includes a gear body, and a plurality of gear teeth extending radially outwardly from the gear body. A gear tooth of the plurality of gear teeth includes two opposing tooth sides extending to a tooth tip. The tooth tip defines a radially outboard extent of the gear tooth. A first tooth side of the opposing tooth sides has a first pressure angle, and a second tooth side of the opposing tooth sides has a second pressure angle different from the first pressure angle.
Claims20
A spur gear of a gearbox of a gas turbine engine system of an aircraft, comprising:
- a gear body;
- and
- a plurality of gear teeth extending radially outwardly from the gear body, a gear tooth of the plurality of gear teeth including two opposing tooth sides extending to a tooth tip, the tooth tip defining a radially outboard extent of the gear tooth;
- wherein a first tooth side of the opposing tooth sides has a first pressure angle;
- and
- wherein a second tooth side of the opposing tooth sides has a second pressure angle different from the first pressure angle.
A gearbox of a gas turbine engine system of an aircraft, comprising:
- a gearbox housing;
- and
- one or more gear arrangements disposed in the housing to transfer rotational energy extracted from a gas turbine engine to one or more accessory components, a gear arrangement of the one or more gear arrangements including a spur gear, the spur gear including:
- a gear body;
- and
- a plurality of gear teeth extending radially outwardly from the gear body, a gear tooth of the plurality of gear teeth including two opposing tooth sides extending to a tooth tip, the tooth tip defining a radially outboard extent of the gear tooth;
- wherein a first tooth side of the opposing tooth sides has a first pressure angle;
- and
- wherein a second tooth side of the opposing tooth sides has a second pressure angle different from the first pressure angle.
A gas turbine engine system of an aircraft comprising:
- a gas turbine engine;
- and
- a gearbox operably connected to the gas turbine engine, the gearbox including:
- a gearbox housing;
- and
- one or more gear arrangements disposed in the housing to transfer rotational energy extracted from a gas turbine engine to one or more accessory components, a gear arrangement of the one or more gear arrangements including a spur gear, the spur gear including:
- a gear body;
- and
- a plurality of gear teeth extending radially outwardly from the gear body, a gear tooth of the plurality of gear teeth including two opposing tooth sides extending to a tooth tip, the tooth tip defining a radially outboard extent of the gear tooth;
- wherein a first tooth side of the opposing tooth sides has a first pressure angle;
- and
- wherein a second tooth side of the opposing tooth sides has a second pressure angle different from the first pressure angle.
Dependencies are inferred from the claim text.